AMERICAN PUBLIC UNIVERSITY SYSTEM Charles Town, West Virginia HIGH LIFT ENTRY VEHICLE DESIGN FORLANDING HIGH MASS PAYLOADS ON MARS A thesis submitted in partial fulfillment of the requirements for the degree ofMASTER OF SCIENCE in SPACE STUDIES by John Clayton Department Approval Date: ______________The author hereby grants the American Public University System the right to display these contents for educational purposes.
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I. INTRODUCTION ...........................................................................................1 II. APPROACH …................................................................................................5
III. MISSION ASSUMPTIONS ..........................................................................24
Launch System …............................................................................................30Reusability …...................................................................................................27Interplanetary Transfer ….................................................................................25Mars Arrival ....................................................................................................27
Aerocapture vs Direct Descent….....................................................................34Landing ….......................................................................................................34
III. VEHICLE DESIGN .......................................................................................24
V. CONCLUSIONS AND FUTURE WORK ....................................................49 LIST OF REFERENCES ...........................................................................................60
LIST OF TABLES TABLE PAGE 1. Physical Education Teacher Demographic Data .......................................................15
2. Current University Student Demographic Data .........................................................17 3. Number of High or Low Value Orientations for Respondents ...................................25 4. Teacher Value Orientation Profile by Gender ...........................................................28 5. Teacher Value Orientation Profile by Academic Rank ..............................................33
6. Teacher Value Orientation Profile by Teaching Experience .......................................39 7. Student Value Orientation Profile by Gender ............................................................41 8. Student Value Orientation Profile by Academic Major ..............................................45 9. Student Value Orientation Profile in Different Year at University ................................51
LIST OF FIGURES FIGURE PAGE 1. Physical Education Teacher Demographic Data ........................................................15
2. Current University Student Demographic Data .........................................................17 3. Number of High or Low Value Orientations for Respondents ...................................25 4. Teacher Value Orientation Profile by Gender ...........................................................28 5. Teacher Value Orientation Profile by Academic Rank ..............................................33
6. Teacher Value Orientation Profile by Teaching Experience .......................................39 7. Student Value Orientation Profile by Gender ............................................................41
For unaccelerated flight conditions, the lift coefficient is given by
C L = W / ½ ρV2S = 2mg / ρV2S
Note that for Mars, g Mars = 0.38 g , and so to be able to apply the X-33 aerodynamic data
to the Mars environment directly, the X-33S reference area must have a scale factor of 0.38 also,which implies a linear scale factor of 0.62. The difference in Reynolds number has a primary
effect on the boundary layer separation characteristics at high angle of attack conditions, and is
highly configuration dependent. Because the main effect is that flow separation of the model
is delayed to a higher angle of attack in the model, validity of the X-33 data for the X-33S near
the maximum angle of attack is a reasonable assumption. The X-33S reference geometry and
aerodynamic parameters are given in table X.X, for a linear scale factor of 0.62, which gives a
vehicle size approximately correct for the Falcon 9 Heavy launch vehicle.
Mars atmospheric entry. A fundamental design trade-off is whether to perform
the EDL directly from the interplanetary approach, or to first enter orbit with an aerocapture
maneuver followed by a subsequent EDL. This trade-off has been well studied, and the result
for capsule entry systems has been in favor of direct EDL. This is largely because the different
thermal protection requirements for aerocapture lead to the necessity of having two separate
heat shields, one for each phase. Newer thermal protection systems (TPS) may make feasible
the use of a single TPS for both aerocapture and subsequent EDL. Advantages of aerocapture
over direct EDL include better characterization of atmospheric conditions prior to EDL, and
more precise EDL targeting. A major consideration of the entry design for manned vehiclesis the need to stay below a 5-g maximum loading for astronauts de-conditioned by the long
interplanetary transit time.
Prior high lift entry vehicle designs. The Earth’s upper atmosphere provides an analog
for testing a Mars entry vehicle. A number of high lift vehicles have been designed for Earth
reentry, including lifting bodies, the space shuttle, and the X-33. These designs provide a wealth
of data on hypersonic aerodynamics, including stability and thermal protection, that is applicable
to Mars EDL.
Landing. This thesis will explore the feasibility of a high lift vehicle that “flies” as long
as possible through the lower Martian atmosphere for deceleration from the hypersonic entry.
Once the angle of attack lift limits are reached, rocket propulsion will provide the additional
lift vector needed to maintain altitude, and provide the final deceleration through a “Pugachev
Cobra” maneuver. That maneuver involves increasing the angle of attack past vertical for final
deceleration, then a return to vertical for landing.
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